Water cooler for aircraft



BEST AVAILABLE com Nov. 2, 1926. 1,605,428

C. DORNER WATER COOLER FOR AIRCRAFT Filed Feb. 14, 1925 (Stn. r j, ly-

@www

BEST AVAILABLE COF.

Patented Nov. 2, 1926.

1 E D'S TATES P cLAUDrUs DORNIER, vor l@FRIEDRICrrsnaimioivrnn;BonENsEEL GERMANY, SIGNOR croira-HALF' To 'noRmER-M'ETALLBAUTENGESELLSCHAFT;Mrr RE- scHRaNRfrER yrnqgirmuire, or FRIEDRrensHArENnNfrnneRonENsE; 1 ger:Ruraux.'

WATER COOLER FOR AIRCRAFT.

' l'Applicationl'ed* February 14,.'1925, Serial No. 9,226', and in Germany \Feh1uary25,f-124 The present .invention relates to water coolersfor .extracting the 'heatwfrom the engine cooling water .on air-craft, .and relates in-particular. to the 'construction of a special kind-of1water cooleriapplied vto the wing ot anaeroplanej. l.. i. .In knownconstructionslotcoolers asap,- plied tosthe wings. of aeroplanescertain .parts ofthe uppenorunderfside of (thewings were formed-gas flat 'hollow bodieswith thin .walls through;,.which the cooling l water, was fconducted.

The; disadvantage z ofthese constructions is mainly that, in order to make the cooling eiectiv'e, comparatively large portions of the wing have to be pressed into service for the purpose. In consequence hereof the danger of leakage is comparatively great and diiculties arise in the building in of these coolers which are integrally connected to the wing. The carrying away of the cooling water in coolers of this kind also causes diiiiculties in connection with mechanical principles as in them the fall or head which should exist either does not exist at all or is very greatly reduced.

These disadvantages are avoided by the subject matter of the present invention.

The wing supported cooler according to the present invention is confined in its local arrangement exclusively to the front edge of the wing, to the contour of which it closely approximates. In order to obtain the necessary cooling surface thin metal ribs or gills projecting up from the edge of the wing are employed. The invention provides for two possible forms of construction.

According to one kind portions of the contour of the nose or leading edge of the wing are constructed as thin walled hollow bodies through which the cooling water circulates, while the above mentioned ribs or gills are brought in the form of sheet metal plates into close contact with the outer wall of the hollow body which carries the water so as to ensure the heat being carried away in an efficient manner.

According to the other type of construction the ribs which effect the exchange of heat are themselves constructed as thinwalled hollow bodies through which the water tlows. The cooling water is supplied to these ribs directly by supply or feed pipes and carried Off. again; into@ a i00.11.6"cti,ng.. .tank or courectingppesr fluff: .l @liv- 15; 55 In.the ,main the jlast named type-ofaconstruction a'ords important practical.. advanf tages:` i I The `arrangement if ogficooler tmay `.be

so yconstructed directly that ,it .is in ,110, `way inf4 any Ldf rectt .organici ;connection with ,the 60 .wing notwithstanding that iticloselyapprox.- f y imates to the shape thereof. The cpgler'niay therefore'ibemounted atiany desrltpemt Q11 the .iront .edge et :theaine- -...-`.[t ..S., als@ rossibletoi increase/Snr :decrease .thesaaef .w coo1er--.off.tl.1is\fkinl;twithcuainterfermg 1 with the construction of the wing and'thus adapt it to motors of varying power.

The ribs of the cooler can be readily collected into groups and may be connected together in any desired way. In case of any leakage different elements may thus be easily cut out; The connection between the various groups may be so arranged that they can be operated from the pilots seat or also automatlcally if necessary. In this way it is possible to regulate the temperatures of the cooling water separately and accurately during the flight of the machine. The different groups of coolers or elements may conveniently be arranged in two sections which are mounted symmetrically to the central plane of light on the front edge of both the wings. The advantage of this arrangement is that the cooling system can be in- B5 creased or reduced in size without the centre of gravity having to be shifted..

A constructional example of the subject matter of the invention is shown in the drawing. in which:

Figs. 1 and 2 are a front elevation and plan of an aeroplane provided withthe above described cooling arrangement while,

Figs. 3 and 4 show in side elevation and plan a cooling element in conjunction with a wing.

In Figs. l and 2 is shown a cooler consisting of two sections. The groups are mounted on the two halves a of the wing and each consists of three cooling elements b arranged alongside each other.

The circulating or flow and return pipes c, and 0l may be conveniently mounted inside the contour of the wing so as to produce but little resistance to the air.

The continuous tubular passages f of the different cooling elements b are connected in the vvell known Way to the flow pipes c and return pipes d with stop valves (not shown) laced between them.

The s ape ofi the cooling elem-ents I) is such that they fit accurately to the contour of the leading edge of the Wing a.

The cooler is attached to the Wing so as to be easily detachable therefrom.

I claim 1. A Water cooler for air craft engines comprising a pair of circulating pipes, one of said pipes arranged on the upper surface of an air craft wing and the other arranged on the lower surface of the wing; and a plurality of hollow cooling elements secured at 'each end to 'and in communication with said pipes, `each element having a shape corresponding to the leading edge of the air craft wing and secured on the outside of and to said Wing.

2.' A Water co'oler for air craft engines comprising a circulating pipe arranged on the 'surface of an 'air 'craft wing; and a plu ali'ty 44of hollov'sT cooling elements secured to BEST AVAILABLE com and in communication with said pipe, each element having a shape corresponding to the leading edge of the air craft Wing and Secured on the outside of and to the leading edge of the Wing.

3. A Water cooler for air craft engines comprising a pair of tubes adapted to have water circulated therein; and a plurality of hollow cooling plates connected at each end to said tubes and being in the shape corresponding to the leading edg'e of the air craft Wing, said plates being in communication with said tubes and being secured to the outside of the leading edge of the wing.

4. A Water cooler for air craft engines comprising a pair of tubes adapted to have Water circulated therein; and a plurality of cooling plates connected at each end to said tubes and being in the shape corresponding to the leading edgejof the air craft Wing, said elements andtubes being secured tothe outside of the leading edge of the Wing.

In testimony whereof I affix my signature.

oLAUDrUs D'oRNrER. 

